RU2298512C1 - Device for moving off service lines with detachable coupling - Google Patents

Abstract

FIELD: space rocket launching complexes; quick-release couplings.

SUBSTANCE: proposed device for moving off service lines with release coupling including board plate separable unit has carriage with drive, branch pipe with service lines and branch pipe protection cover with cover displacement mechanism. Branch pipe is installed on carriage by means of balancing device and is furnished with mechanism to lock-butt-joint between branch pipe and separable unit. Balancing device contains spring pneumatic suspensions and spring pneumatic stabilizers of branch pipe. Protective cover of branch pipe with its displacement mechanism is installed in launching table room for holding in closed position by said locking mechanism. Distance between carriage and protective cover of branch pipe in closed position is chosen to provided preliminary compression of spring pneumatic suspensions in interlaunching period. Invention prevents collision of movable parts of device in process of accelerated moving off of branch pipe with separable unit and service line and axial misalignment of branch pipe and protective cover in process of its closing, provides protection of inner spaces of service line branch pipe in interlaunching period from getting of dust and moisture to preclude residual deformation and sagging of springs of branch pipe pneumatic suspensions.

EFFECT: improved reliability in service.

5 dwg

Description

The invention relates to mechanical engineering, and in particular to devices for retracting communications with a detachable connection from the side of the rocket, and can be used in launch rocket and space complexes.

A device for the removal of communications with detachable connection according to the patent of Russia No. 2144464, IPC B65G 53/40.

The device consists of a rotary boom, a drive, a balancing device. A detachable connection includes an onboard board and a detachable unit.

The main disadvantage of the device is the manual connection of communications to a detachable unit, which does not allow automating the processes of docking and removal of communications.

A known device tap with detachable connection according to the patent of Russia No. 2185315, IPC 7 B65G 53/40.

The device comprises a carriage equipped with a drive, a pipe with communications, equipped with a locking mechanism for the joint and a balancing device. The detachable connection includes an onboard payload of the ILV (space rocket) and a detachable unit. In the specified device provides automation of the processes of docking and removal of communications.

The mass of the detachable unit is commensurate with the mass of the nozzle, and the stiffness of the spring elements of the balancing device is selected from the condition of balancing only the nozzle with communications when docking with the detachable detachable connection block to ensure the transfer of minimum loads to the onboard ILV board.

The undocking and removal of the detachable unit, mounted on the nozzle, is carried out at the initial stage of the launch of the rocket launcher, while for the removal to a safe distance into the launch pad room, an accelerated withdrawal mode is required. In this regard, after undocking, an accelerated downward movement of the detachable unit with the pipe and communications and a significant shock loading of the spring elements of the balancing device occur, while in the process of accelerated removal, the movement of the moving parts of the device is carried out according to the law of damped oscillations of a mechanical system with several degrees of freedom.

In addition, in the interstarting period, the suspension springs are loaded for a long time with the mass of the pipe with communications, while over time this leads to permanent deformation and settlement of the springs.

Another disadvantage of this device is the insecurity of the internal communication cavities of the pipe in the idle position from dust and moisture.

These disadvantages are eliminated in the proposed device by the fact that additional spring air suspensions and spring pneumatic stabilizers of the nozzle are introduced, and the protective cover of the nozzle with the mechanism for moving it is installed in the launcher room, and the distance between the carriage and the protective cover in its closed position is selected based on the condition of being in the interstart the period of the spring air springs in the preload position.

Thus, in the proposed device:

1. Due to the introduction of spring air suspensions and spring air stabilizers:

- provided spatial fixation of the pipe with a detachable unit and communications in the process of their accelerated removal, while eliminating the collision of the moving parts,

- provided spatial fixation of the pipe in the retracted position of the device during the closing of the protective cover, eliminating misalignment of the pipe and protective cover.

2. Due to the installation of the protective cover of the nozzle with the mechanism of its movement in the launcher room, the distance between the carriage and the protective cap of the nozzle in its closed position is selected based on the condition that the spring air suspensions are in the pre-preload position during the inter-launch period:

- protection of the internal cavities of the branch pipe communications during the inter-launch period from dust and moisture;

- elimination of residual deformation and precipitation of the springs of the suspension pipe.

The drawings show:

- figure 1 - device retraction in its original position;

- figure 2 - device retraction in the initial position with the protective cover of the pipe open;

- figure 3 - device tap in the docked position;

- figure 4 - device retraction in the designated position;

- figure 5 is a view a of figure 2.

The communications outlet device with a detachable connection consists of a pipe 1 (Fig. 1) installed by means of a balancing device on the carriage 2. The balancing device consists of four hinge rods 3, two air suspensions 4 and two air stabilizers 5. The air suspension consists of cylinder 6 (Fig. 5 ), a rod 7 with a piston 8, a spring 9. The cylinder 6 and the rod 7 are provided with spherical bearings 10. The pneumatic stabilizer 5 (Fig. 1) consists of a bracket 11 (Fig. 5), in which the cylinder 12 with the rods 13, 14 and pivotally mounted the piston 15. The rod 13 is equipped with a spring 16. N Pivot 11 is pivotally mounted lever 17 with the roller 18 and is pivotally connected to a rod 14 of the cylinder 12. The air suspension 4 (1) and provided with fittings pnevmostabilizatory 5 "SH1" (Figure 5) and "W2".

The carriage 2 (figure 1) is installed in the rollers 19, rigidly mounted on the side walls of the room in the supports 20 of the launch table 21, and is equipped with a drive 22, the rod of which is pivotally connected to the carriage 2, and the housing is pivotally connected to the support 23 of the launch table 21. B the support 24 is rigidly fixed to the buffer 25. The pipe 1 is equipped with guide pins 26, grippers 27 and pipelines 28 to which flexible communications 29 are attached.

In the premises of the launch pad 21, a protective cover 30 of the pipe 1 is pivotally mounted with a mechanism for its movement, consisting of a drive 31, a lever device 32 and a latch 33.

On ILV 34, a detachable block 36 of the onboard connector is secured to the on-board board 35 along the “a” plane, provided with sealing elements of the connecting lines along the “a” and “b” planes.

In the initial position, the carriage 2 (Fig. 1) with the pipe 1 and communications 29 is in the retracted position, the protective cover 30 is closed and held by the grippers 27, while the force required to protect the internal cavities of the pipe 1 from dust and moisture, as well as to maintain the mass of the pipe 1. The mass of the pipe 1 with communications is perceived by a lever device 32 mounted on the ceiling of the launch pad 21. The rods 7 (Fig. 5) of the air suspension are in the extended position, and the springs 9 spring suspensions - in the preload position. The longitudinal axis of the pipe 1 (figure 1) is aligned with the longitudinal axis of the protective cover 30 and is located at a distance "in" from the carriage. The carriage 2 is located at a distance of "g" from the longitudinal axis of the detachable block 35.

Communications docking operations are performed automatically.

Compressed air is supplied to the “Ш1” fittings (Fig. 5) of spring air suspension 4, while the air suspension provides a force exceeding the mass of the pipe 1 with communications 29. Compressed air is supplied to the “Ш2” fittings of the spring pneumatic stabilizers 5, while the orientation of the pipe 1 in transverse direction so that the plane formed by the axes "g" and "c" is vertical. The grippers 27 are opened, releasing the protective cover, while the distance “c” from the longitudinal axis of the nozzle to the carriage does not change. Compressed air is supplied to the actuator 31, by means of the lever device 32, the protective cover 30 of the pipe 1 opens (Fig. 2) and is locked in the open position by the latch 33. Compressed air is drained from the spring air suspensions 4 and spring air stabilizers 5, while the longitudinal axis of the pipe 1 is aligned with the longitudinal axis of the detachable unit 35, and the mass of the pipe 1 with communications 29 is perceived by the springs of spring air suspensions 4. The springs of spring air suspensions are in the position of the working preload. Compressed air is supplied to the drive 22, the carriage 2 in the rollers 19 moves in the direction of joining, the pins 26 of the nozzle 1 go into the guide bushings of the detachable block 36, the nozzle is oriented relative to the detachable block by means of a balancing device including 4 hinged rods 3, spring air suspension 4 and spring pneumatic stabilizers 5, docking is carried out, after which the grippers 27 are closed, providing the necessary force to seal the docked lines of the pipe 1 and the detachable block 36 (Fig.3) along the plane ". After that, ILV refueling is carried out.

Undocking and withdrawal of communications are carried out at the initial stage of the ILV lift. Some time before the launch of the rocket engines, compressed air is supplied to the drive 22 of the carriage 2 in the direction of withdrawal, while undocking is not performed due to the fact that the detachable block 36 and the side plate 35 of the rocket carrier 34 are connected by a lock along the “a” plane, and the pipe 1 locked relative to the detachable block grippers 27 on the plane "b". Compressed air is supplied to the spring air suspension 4 and spring air stabilizers 5, while a force is applied to the pipe 1 and the detachable unit 35 in the direction of the ILV lift.

In this position, the device is in readiness for undocking, while the necessary gases continue to flow on board the ILV. After the launch of rocket engines and the start of the lift of the rocket launcher, the withdrawal device through the articulated rods 3 and spring air suspensions monitors the rise of the rocket. At a certain height of elevation, pyromedics of the side plate 34 are triggered, a lock is opened connecting the side plate 35 and the detachable block 36 along the “a” plane, after which the pistons 8 (Fig. 5) and 15 spring air suspensions 4 and spring air stabilizers 5 are moved under the action of compressed air to the stop in the cylinders 6, 12, providing spatial fixation of the detachable block 35 with the pipe 1 and communications 29. Under the action of the drive 22, the carriage in the accelerated mode moves in the direction of the outlet, while the energy of the carriage outlet is extinguished by the buffer 24 (Figure 4). Compressed air is drained from all drives of the device.

After the launch of the rocket launcher, work is carried out to bring the device to its original position, for which the grippers 27 of the pipe 1 are opened, the detachable unit 36 is evacuated, compressed air is supplied to the air suspension 4 and the air stabilizers 5, while the pistons 8 (Figs. 5, 4) and 15 they move to the stop in the cylinders 6, 12, providing spatial fixation of the nozzle, and the longitudinal axis of the protective cover 30 coincides with the longitudinal axis of the pipe 1, after which the latch 33 (Fig. 1) of the open position of the protective cover opens, compressed air is supplied to the actuator 31 , the protective cover 30 of the pipe 1 closes, after which the grippers 27 are closed, while the sealing elements provide the force necessary to protect the internal cavities of the pipe 1 from dust and dirt, as well as to hold the mass of the pipe 1 with communications 29, after which the compressed air from the gripper drives 27, the cover 30, the air suspension 4 and the pneumatic stabilizers 5. This ensures the size "between" the carriage 2 and the longitudinal axis of the pipe 1, and the spring springs are in the pre-position preload.

Thus, in the proposed device provides:

- spatial fixation of the pipe with a detachable unit and communications in the process of their accelerated removal, while eliminating the collision of moving parts;

- spatial fixation of the pipe in the retracted position of the device during the closing of the protective cover, eliminating the misalignment of the pipe and protective cover;

- protection of the internal cavities of the branch pipe communications during the inter-launch period from dust and moisture;

- elimination of residual deformation and precipitation of the springs of the suspension pipe.

Claims (1)

A communications tap with a detachable connection including an onboard board and a detachable unit containing a carriage equipped with a drive, a communications pipe mounted on the carriage by means of a balancing device and equipped with a locking mechanism for the joint between the pipe and the detachable unit, characterized in that the balance device is additionally spring air suspensions and spring pneumatic stabilizers of the nozzle are introduced, and the protective cover of the nozzle with a mechanism is introduced into the structure of the exhaust device m of its movement, installed in the launcher room with the possibility of holding it in the closed position by the aforementioned locking mechanism, the distance between the carriage and the nozzle protective cover in its closed position being selected based on the condition that the spring air suspensions are in the pre-launching period in the pre-start position.

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